榫连结构的高应力梯度及破坏分析

魏大盛; 王延荣

榫连结构的高应力梯度及破坏分析

北京航空航天大学能源与动力工程学院, 北京 100191

基金项目: 凡舟青年科研基金资助项目(20080403)

详细信息

作者简介:
魏大盛(1978-),男,黑龙江宁安人,讲师,dasheng.w@163.com.

中图分类号: V 231.91; V 232.3
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- 文章访问数: 2951
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- 被引次数: 0
出版历程
- 收稿日期: 2009-08-07
- 网络出版日期: 2010-10-31

On the high stress gradient and failure analysis of dovetail attachments

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 某燕尾形榫连结构的分析表明叶盘榫齿/榫槽接触区边缘存在较高的应力梯度,接触应力的有限元解同网格疏密程度密切相关.通过建立一系列不同密度网格的模型,对此问题展开有限元建模分析,以改善接触应力的求解精度,同时深入讨论材料弹塑性对接触应力的影响.在弹塑性接触应力分析的基础上,采用断裂力学方法建立了榫连结构高应力梯度位置的破坏分析模型,判断裂纹的萌生及扩展方向,以进行结构的强度及寿命分析.
- 榫连结构 /
- 高应力梯度 /
- 破坏 /
- 裂纹萌生 /
- 断裂力学
Abstract: Studies reveals that high stress gradient exists near the edges of contact in dovetail attachment, of which the numerical solution to contact stress depends on finite element (FE) mesh density. So a set of FE models with different mesh of dovetail attachment were used to analyze the effect of FE modeling on improving the solving accuracy of contact stress. Then the effect due to elasticity and plasticity of materials was discussed. On the basis of elastic-plastic contact stress, a fracture model on the part with high stress gradient was established by means of fracture mechanics, which can be used to determine the direction of crack initiation and propagation and more to evaluate the structural strength and lives.
- dovetail attachment /
- high stress gradient /
- fracture /
- crack initiation /
- fracture mechanics

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参考文献(1)

[1] 何明鉴.机械构件的微动疲劳[M].北京:国防工业出版社,1994 He Mingjian.Fretting fatigue of component[M].Beijing:National Defense Industry Press,1994(in Chinese) [2] 温卫东,高德平.榫头/榫槽接触问题边界元分析[J].航空动力学报,1992,7(2):117-120 Wen Weidong,Gao Deping.Analysis of tenon and mortise contact problems by boundary element methods[J].Journal of Aerospace Power,1992,7(2):117-120(in Chinese) [3] 郑旭东,蔚夺魁,王兆丰,等.某型航空发动机涡轮叶片和轮盘榫齿裂纹故障力学分析[J].航空发动机,2005,31(3):35-38 Zheng Xudong,Yu Duokui,Wang Zhaofeng,et al.Mechanical analysis of crack failures in turbine blade and disk serration of an aeroengine[J].Aeroengine,2005,31(3):35-38(in Chinese) [4] Sinclair G B,Cormier N G,Griffin J H,et al.Contact stresses in dovetail attachments:finite element modeling[J].Journal of Engineering for Gas Turbines and Power,2002,124:182-189 [5] Sinclair G B,Cormier N G.Contact stresses in dovetail attachments:physical modeling[J].Journal of Engineering for Gas Turbines and Power,2002,124:325-331 [6] Sinclair G B,Cormier N G.Contact stresses in dovetail attachments:alleviation via precision crowning[J].Journal of Engineering for Gas Turbines and Power,2003,125:1033-1041 [7] 古远兴.高低周复合载荷下燕尾榫结构微动疲劳寿命研究 .南京:南京航空航天大学能源与动力学院,2007 Gu Yuanxing.Research on fretting fatigue life of dovetail joint under HCF-LCF load .Nanjing:School of Power and Energy,Nanjing University of Aeronautics and Astronautics,2007(in Chinese) [8] 刘道新,刘军,刘元镛.微动疲劳裂纹萌生位置及形成方式研究[J].工程力学,2007,24(3):42-47 Liu Daoxin,Liu Jun,Liu Yuanyong.Study on nucleating location and formation of fretting fatigue cracks[J].Engineering Mechanics,2007,24(3):42-47(in Chinese) [9] 魏大盛,王延荣.榫连结构接触面几何构形对接触区应力分布的影响[J].航空动力学报,2010,25(2):407-411 Wei Dasheng,Wang Yanrong.Effects of the profile of contact surfaces on the stress distribution for tenon jointing in bladed-disk assemblies[J].Journal of Aerospace Power,2010,25(2):407-411(in Chinese) [10] Golden P J,Calcaterra J R.A fracture mechanics life prediction methodology applied to dovetail fretting[J].Tribology International,2006,39:1172-1180

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